Thales Avionics Limited 2010

ESA ANTARES CA UT StudyWill Birkinshaw27 May 2010

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Introduction

Design aims Certification and installation time line Performance targets UT Block Diagram Installation constraints Antenna installation configuration DLNA/HPA/Modem configuration options Prototype development

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Design Aims

Able to carry COCR traffic in parallel with L-DACS Must work as well as or better than VHF

Must be available during aircraft manoeuvres Holding stacks etc.

Must be available when satellite elevation is low Northern Trans-Atlantic routes Northern Europe

CA UT to be certified to DAL level C UT to be capable of being an HF replacement

Must work as well as or better than HF Must be capable of operation in a dual redundant system

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Certification and Installation time line

System development phases and indicative time to key milestones

~20 years

Time lines from previous Avionics Systems Certifications:-Early Trials 1952, TCAS programme launched 1981, mandatory in USA 1993.ADS-B RTCA DO242 specification 2002, mandatory 2020L Band Satcom System Definition Manual ~1987, TSO-C132 2004 (non-mandatory system),

Standardisation

Technology Evaluation

Infrastructure Certification

Avionics deployment

Selection of Future System

Airworthiness certification of first operational aircraft

System full operational capability

Deadline for mandatory fit

Fixed and space infrastructure implementation

Includes UT and fixed system evaluation

Generic and Satellite System specific standards

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UT Performance targets

The ideal target is to achieve full spherical coverage from the airframe whilst maintaining the following parameters:-

Achieve the defined EIRP (nominally 0dBic)Achieve the defined G/T Ability for fitment to all commercial airframesEquipment certified to DAL level CSome compromise from this ideal coverage target will be required if the UT is to be acceptable to airframe manufactures and from a cost and reliability viewpoint. Compromise options include:-Reduction in the acceptable coverage of the UT at the defined EIRP and G/T levels.Reduction in the EIRP and G/T requirements.

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UT Block Diagram

Antenna 1

DLNA

HPA

RF TX RF RX

MUX/DEMUX

Modem/AvionicsProcessing

Basic functional blocks of the UT showing a possible antenna switching option.

Locations on an airframe

Outside the fuselage

Cabin area/crown area

Cockpit/EEbay

Antenna 2(Optional)

DLNA

switch

Switch or mixerVery close to antenna

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Installation constraints

Airframe imposed limitations Minimise the number of antennas required. Minimise the antenna height and profile. Maintain minimum distance from other antenna installations Comply with certification requirements Airframe specific location limitations

Availability of adequate space adjacent to antenna inside the airframe Antenna location must not infringe non-ionising radiation limits UT should not require the external forced cooling air

System imposed limitations System EIRP and modulation scheme dictates the heat required to be

dissipated from LRUs. Other constraints

Interchangeability and standardisation of LRUs and interfaces

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Antenna installation configuration #1

The preferred individual antenna option is a Low Gain fix beam antenna.(Nominal gain 0dBic).

Advantages:- Simplicity, small size and weight, low cost, high reliability, low stress on airframe.

Disadvantages:- low gain hence low radiated RF power levels if HPA power not increased to compensate

Antenna system options:-Single antenna Advantages:- minimal effect on airframe, low cost, suited to small airframes. Disadvantages:- No antenna redundancy, restricted system availability.

Dual antenna Advantages:- Can offer dual redundancy or can be used to improve coverage. Disadvantages:- cannot offer acceptable coverage and dual redundancy simultaneously.

Higher cost than single antenna. More difficult to fit on smaller airframes.

Multiple antennas (4) Advantages:- offers improved coverage and dual redundancy. Disadvantages:- Higher cost, more difficult installation and more significant impact on

airframe design.

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Antenna installation configuration #2

A380

CRJ200

AVRO RJ

Falcon 100

A320

13m80m

Aircraft simulation models

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Antenna installation configuration #3

AVRO RJ Fuselage top front

Single antenna coverageHigher gain towards red

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Antenna installation configuration #4

AVRO RJ Fuselage top rear

Single antenna coverageHigher gain towards red

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Antenna installation configuration # 5

CRJ Fuselage top middle

Single antenna coverageHigher gain towards red

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Antenna installation configuration # 6

CRJ Fuselage top rear

Single antenna coverageHigher gain towards red

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Antenna installation configuration # 7

A320 Fuselage top front

Single antenna coverageHigher gain towards red

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Antenna installation configuration # 8

A320 Fuselage top middle

Single antenna coverageHigher gain towards red

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Antenna installation configuration #10

A320 Fuselage top front fuselage side

Single antenna coverageHigher gain towards red

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DLNA/HPA/Modem configuration options

Considerations:- RF loss to antenna(s) Amount of heat to be dissipated Space available – limits physical size of modules Adequate air flow in proposed locations Number of antennas to be supported.

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DLNA/HPA/Modem configuration options

AIRCRAFTDATA

INTERFACES

AIRCRAFTDATA

INTERFACES

Modems located in Avionics Bay

One potential 2 antenna configuration option

MODEMAND

AVIONICSPROCESSOR

DUC_TX

DDC_RX

MUX/DEMUXHigh Speed

Serial Interface

RF_RX ADC

ANTENNA 1

DLNA

HPA RF_TX

RF_RX

DAC

ADCMUX/DEMUXHigh Speed

Serial Interface

ANTENNA 2

MODEMAND

AVIONICSPROCESSOR

DUC_TX

DDC_RX

MUX/DEMUXHigh Speed

Serial Interface

High Speed Serial InterfacePotentially Fibre Optic ring network

preventing single point failure.

Redundant Backup System

RF_RX ADCDLNA

HPA RF_TX

RF_RX

DAC

ADCMUX/DEMUXHigh Speed

Serial Interface

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Prototype development in Phase B

Antares UT prototype hardware to be built in modular form to facilitate construction and testing.

Prototype HPA, RF modules and modem will be produced . The prototypes will be developed to demonstrate operation of

the system physical layer and will communicate with the Verification Test Bench.